Aerospace Engineering > GATE 2017 > Aircraft Stability
The roots obtained by solving longitudinal characteristic equations of motion for a statically stable aircraft are given below:
λ.1,2=-0.02±0.30i, λ.3,4=-2.00±2.50i, where i=√-1
The undamped short-period longitudinal natural frequency (radians/sec) and damping ratio, in that order, are close to
λ.1,2=-0.02±0.30i, λ.3,4=-2.00±2.50i, where i=√-1
The undamped short-period longitudinal natural frequency (radians/sec) and damping ratio, in that order, are close to
Correct : d
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